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Aerospace and Navigational Electronics, IEEE Transactions on

Issue 0 • Date Oct. 1963

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Displaying Results 1 - 25 of 64
  • Tenth Annual East Coast Conference on Aerospace and Navigational Electronics

    Publication Year: 1963 , Page(s): c1
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  • Technical Papers

    Publication Year: 1963 , Page(s): i - ii
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  • Chairman's Message

    Publication Year: 1963 , Page(s): iii
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  • [Table of contents]

    Publication Year: 1963 , Page(s): iv - ix
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  • Introduction

    Publication Year: 1963 , Page(s): xi
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  • Radiation Effects - I

    Publication Year: 1963 , Page(s): 1.1-1
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  • Space Vehicle Attitude Control

    Publication Year: 1963 , Page(s): 1.2-1
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  • A Planetary Orbiting Relay Communication Link for Project Voyager

    Publication Year: 1963 , Page(s): 1.3.1-1 - 1.3.1-8
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    Beginning in the late 1960's Voyager spacecraft will be launched to Venus and Mars. These spacecraft may contain both orbiting and landing modules. One of the first questions which arises in such a system is whether to transmit the data originating in the lander directly back to earth or to relay through the orbiter. This paper discusses the theoretical, operational and environmental aspects of the problem and concludes that a relay link is definitely required for Venus and would be advantageous for Mars. A 100-mc carrier frequency for the relay link is recommended, and the results of comparisons of promising modulation and multiplexing techniques are presented. View full abstract»

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  • Electronic Solar Flare Alarm System

    Publication Year: 1963 , Page(s): 1.3.2.1 - 1.3.2.15
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    This paper describes the work done in designing and breadboarding a solar flare alarm system employing video digital techniques. The conceptual design of the system is presented, and experimental apparatus, solar and flare simulation equipment, and procedures employed in obtaining performance data are described. Experimental measurements and results are included. In general, it was found that the system is capable of detecting simulated flares whose contrast exceeds that of the immediate solar background by a factor of 1.5 to 2.0. Positional linearity in determining the precise location of the flare on the solar disc is within ± 2.5%. Spurious signal generation in the system due to vidicon amplifier noise and noise in the counter circuitry was found to be less of a problem than had been anticipated. View full abstract»

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  • Electrical Solar Power Supply Systemi Considerations for UK-2/S-52 International Satellite

    Publication Year: 1963 , Page(s): 1.3.3-1 - 1.3.3-3
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    The UK-2/S-52 Satellite is one of NASA's International Satellites and carries Experiments built by the British. The satellite is under Management and technical supervision of Goddard Space Flight Center. The Consideration and analysis of environmental and operational requirements, as well as the requirements imposed by the satellite configuration, influenced the UK-2/S-52 power source system design, the detail specifications for the batteries and solar paddles, and the testing of these and associated sub-assemblies. For example, early appreciation for the influence of temperature extremes, as well as of the effects of the load on the external characteristics of the unregulated bus resulted in the faithful simulation of operational influences at the electrical functional testing level and individual unit qualification testing level of components supplying or using the unregulated bus. In discussing some of these considerations, this paper describes the UK-2/S-52 power supply from a functional standpoint and includes a discussion of the load analysis results and some of the performance characteristics of the solar paddles, the main batteries, and the power source control and protective circuits. Also discussed are significant routines of the test procedures for paddles and batteries as well as some of the test results. View full abstract»

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  • Radar System Design for Spacecraft Terminal Control

    Publication Year: 1963 , Page(s): 1.3.4-1
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    This paper discusses the design of radar for use in the terminal control of manned and umanned space vehicles of the maneuverable type. In order to present the requirements and specifications of the required radar, the type of missions that will use terminal control are discussed. Also terminal control equipment suchl as analogue computers and displays are mentioned in preserting these specifications. The main body of the paper deals with specific areas of radar development resulting from recent work in developing a terminal control system for the umanned X-20 vehicle. The technical areas discussed are reliability of self-acquisition, pulse code modulated (PCM) data transmission, semidigital ranging, and the accuracy of computed velocity, altitude and positional data. View full abstract»

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  • The UK-2/S-52 International Satellite

    Publication Year: 1963 , Page(s): 1.3.5-1 - 1.3.5-3
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    The S-52 (See Figure 1) is being built under the cooperative international program being conducted by the United States and the United Kingdom. In the U.K., University and Government, Laboratories designed and constructed the instrumentation for the S-52 experiments under the scientific direction of the British National Committee for Space Research. The Goddard Space Flight Center, for NASA, has overall U.S. responsibility for the program including the design, development, construction, and testing of the spacecraft as well as launching, tracking, and data acquisition phases. GSFC has contracted to Westinghouse the building of the spacecraft structure, the design and manufacture of certain satellite subsystems, the integration of all subsystems into an operating satellite, and assistance in environmental proof testing of completed satellites. The NASA Langley Research Center is responsible for the launch vehicle system. The launching will take place at Wallops Island, Va. during 1963 utilizing a Scout Vehicle. The satellite will be laumched into an orbit with an apogee of approximately 810 n.m., a perigee of approximately 150 n.m. and with an inclination of 51°. View full abstract»

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  • Microelectronic Devices for Application in Transient Nuclear Radiation Environments

    Publication Year: 1963 , Page(s): 1.4.1-1 - 1.4.1-6
    Cited by:  Papers (2)
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    The results of environmental tests designed to determine the relative susceptibility of monolithic silicon and thin fillm integrated circuits and devices to the transient nuclear radiation environment associated with a nuclear explosion are discussed. These results strorngly indicate that hybrid thin film circuits employing high frequency transistors should be used in systems now being designed which require microelectronic circuitry to operate in a transient radiation environment. Tests conducted on experimental devices indicate that the insulated- gate thin-film field effect transistor is less affected by transient nuclear radiation than any other active microelectronic device presently available. When the insulated gate field effect device becomes commercially available, it should provide complete thin film integrated circuits which are highly resistant to transient nuclear radiation. View full abstract»

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  • Test Techniques for Transient Radiation Effects

    Publication Year: 1963 , Page(s): 1.4.2.1 - 1.4.2.12
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    This paper gives examples of specific test techniques which have been used in performing transient radiation effects test measurements. The techniques were developed primarily for use with electron linear accelerators but can be applied directly in flash X-ray and pulsed reactor test programs as well. View full abstract»

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  • An Estimate of Radiation Effects on Electronic Compoents for the Lunar Excursion Module

    Publication Year: 1963 , Page(s): 1.4.3-1 - 1.4.3-11
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    The various radiation sources (solar flares and natural and artificial Van Allen Belts) to be encountered on the Apollo Mission have been compared with regard to effect on electronic components. It is found that a large Class 3+ flare constitutes the most serious hazard. We have assumed that such a flare will occur and have calculated the degradation in performance of electronic components caused thereby. Resistors and capacitors are unaffected but transistors are seriously affected. Example: unshielded 50 mc Si and 10 mc Ge transistors will experience gain reduction to 70% of initial; transistors of lower cutoff frequency will experience a proportionately greater reduction. A one gm/cm2 Al shield reduces the damage by a factor of 4 in Si and 5 in Ge transistors. View full abstract»

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  • Selection of Radiation Qualified Semiconductor Electronics for Space System Design

    Publication Year: 1963 , Page(s): 1.4.4-1 - 1.4.4-7
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    Factors controlling the evaluation of radiation vulnerability of transistors, diodes, and solar cells are reviewed. Typical results from computer analysis of transistor current gain degradation are presented, emphasizing dependence of degradation on dc operating point. Particle equivalence for permanent radiation damage in semiconductor devices is summarized. Extention of operational lifetime of space system electronics is also discussed. View full abstract»

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  • A Nuclear Radiation Resistant Control Moment Gyroscope

    Publication Year: 1963 , Page(s): 1.4.5-1 - 1.4.5-8
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    The nuclear radiation resistant control moment gyroscope is a sensing and control device intended for service in space vehicles with nuclear radiation environment. Its main function is to control the altitude and stability of a spacecraft in orbit. The nuclear radiation resistance is achieved through the highly selective use of radiation resistant materials in the design. One such gyro has been ground tested in a nuclear radiation environment. View full abstract»

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  • Digital Attitude Control System for Spacecraft

    Publication Year: 1963 , Page(s): 1.5.1-1 - 1.5.1-10
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    For attitude control of certain classes of spacecraft, digital techniques appear to offer distinct advantages over analog systems. A program was conducted to evaluate experimentally a stabilization and control system in which digital methods are used for measurement, signal processing, and torque control. The logic design of the control system is discussed in detail, and the hardware used for implementing the design is described. Preliminary experimental results are presented which confirm predicted control accuracy advantages. View full abstract»

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  • Fine Pointing Control for the Orbiting Astronomical Observatory (Oao)

    Publication Year: 1963 , Page(s): 1.5.2-1 - 1.5.2-5
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    High pointing accuracy requirements are imposed on the control system of the OAO. One tenth arcsec angular accuracy can be achieved in orbiting spacecraft using star references, long focal length optical systems, and relatively small torquing devices. Noise problems are introduced when a single error sensor is required to track stars with greatly different magnitudes. As star magnitude decreases, the compensating increase in the gain by the automatic gain control decreases the signal-to-noise ratio and degrades the pointing accuracy. A linear range of at least one arcmin will eliminate or reduce many restrictions on initial acquisition of a particular star. These restrictions are introduced by high initial satellite rates and/or unbalanced inertial wheel torques. Relatively small voltage rates out of the sensor may be detected by a suitably designed nonlinear lead circuit with low frequency corners. View full abstract»

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  • An Attitude Control System for the Advanced Orbiting Solar Observatory

    Publication Year: 1963 , Page(s): 1.5.3-1 - 1.5.3-3
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    First Page of the Article
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  • Fine Sun Tracker for Advanced Orbiting Solar Observatory

    Publication Year: 1963 , Page(s): 1.5.4-1 - 1.5.4-10
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    The analysis and design of a fine sun tracker for the Advanced Orbiting Solar Observatory are discussed. The tracker provides accurate pointing information in pitch and yaw, permitting precise static and dynamic orientation of the observatory with respect to the sun's apparent disc, in accordance with ground commands. The tracker uses a servo driven optical slab in each axis to offset the optical null by the required amount. The error signal thus developed in a pair of matched silicon photo-voltaic cells is fed to the observatory control system, to produce the desired orientation in that axis. The essential features of the tracker design are incorporated in a breadboard model. The performance of this model verifies the inherent capability of the design to achieve a 2 are-second r.m.s. pointing accuracy. View full abstract»

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  • A Stability Criterion for an Artificial Earth Satellite

    Publication Year: 1963 , Page(s): 1.5.5-1 - 1.5.5-10
    Cited by:  Papers (1)
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    The equation of rotation of the spacecraft about a set of control axes are developed to reveal the required functions of a momentum exchange control system when subjected to external disturbances. A linear control system is designed and the three-axis characteristic equation is developed. This ninth order equation has coefficients which vary with the particular attitude references in use, and with the particular desired attitude. The number of and location of the references are variables. Reference information and commanded attitude data are lumped into two constants and lines of constant minimum system damping are plotted parametricly. Thus before slewing to a new attitude, the degree of damping or instability may be readily determined. View full abstract»

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  • Piloted Flight Simulation

    Publication Year: 1963 , Page(s): 1.6.1
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  • Space Eivironment

    Publication Year: 1963 , Page(s): 2.1.1 - 2.1.2
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  • Gemini Range and Range Rate Measuring System

    Publication Year: 1963 , Page(s): 2.2.1-1 - 2.2.1-8
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    To complete the terminal phase of a space rendezvous mission, it is essential that accurate indications of target vehicle range and relative range rate be presented to the astronauts commanding the chaser vehicle. The indicator characteristics and the method of data presentation assume prime importance in compliance with the above. Therefore, a discussion is given of the logical development and function of the indicator. Having established the indicator format the discussion proceeds with a description of the mechanization of the range and range rate circuitry incorporated in the GEMINI Rendezvous Radar. In this section, details are given which describe the methods by which data, extracted from the received signals, are processed in analog form suitable for application to the indicator. View full abstract»

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Aims & Scope

This Transactions ceased publication in 1965. The new retitled publication is IEEE Transactions on Aerospace and Electronic Systems.

Full Aims & Scope